Propeller

ABSTRACT

The inventive propeller consists of a shaft comprising at least two hubs which are mounted thereon and provided with blades fixed to each of them. Each blade has a front and rear sharp edges and is embodied in such a way that the greater airfoil thickness thereof is equal to (0.10-0.25)b along the blade span, wherein b is the mean chord of the blade. The greatest airflow thickness of each blade is located in the middle of each mean chord and is twisted around an axis passing through the middles of the mean chords along the blade span. The blade can be fixed to each hub at an angle of &lt;90° with respect to the radius thereof, thereby reducing a local aerodynamic drag and aerodynamic loads. The inventive propeller can be provided with a fixed cylindrical enclosure which embraces all blades and extended in front of the blades of the front hub at a distance which is equal to or greater than the blade span, thereby increasing a torque effect value.

TECHNICAL FIELD

The invention relates to propeller, which can be used in the area of aviation and special transportation (propeller-sleighs sled, air-support vessels).

PRIOR ART

A propeller is known, which has a shaft with two hubs installed on it, with blades which are fixed on each of the hubs uniformly over a circumference. The blades on the two hubs are driven in rotation in opposite directions by means of an motor (U.S. Pat. No. 2,953,320 IPC: 244-12, 1960).

A propeller is known, which has a shaft with two hubs installed on it, with blades fixed on each of the hubs uniformly over a circumference. The blades of the two hubs are driven in rotation in opposite directions by means of a motor (RU patent no. 2,062,246, IPC:B 64 C29/00, 1996).

The disadvantage of both known propellers is that each design of the propeller generates high aerodynamic loads which act on it, that leads to a necessity to provide its high strength and stiffness.

SUMMARY OF THE INVENTION

A task which is solved in this invention is to create a propeller which provides a reduction of aerodynamic loads acting on it.

This task during the creation of propeller is achieved in that, in the propeller which has a shaft with at least two hubs installed on it with blades fixed on each of the hubs uniformly over a circumference, each blade has sharp front and rear edges, and is formed along an extension of a blade with a maximum thickness of profiles (0.10-0.25)b, where b is a length of a local chord of the blade and twisted relative to an axis extending through a middle of the local chords along the extension of the blade, wherein the maximum thickness of the profile is located in a middle of each local chord.

The arrangement of at least two hubs with blades fixed on each of them uniformly over a circumference leads to a reduction of sizes of the hubs with the blades, which leads to a reduction of aerodynamic loads acting on the propeller.

The sharp front and rear edges of each blade together provide a reduction of aerodynamic resistance of the blades and as a result a reduction of aerodynamic loads acting on the propeller.

The configuration along an extension of each blade with the maximum thickness of the profiles (0.10-0.25)b, wherein b is a length of local chord of the blade, provides within a selected range of the maximum thickness of the profiles, a reduction of aerodynamic resistance of the blades and as a result a reduction of aerodynamic loads acting on the propeller.

The maximum thickness of the profile of each blade, located in the middle of each local chord, provides a uniform distribution of aerodynamic loads along the length of the chord (width of the blade), which reduces aerodynamic loads acting on the propeller.

Twisting of each blade relative to an axis, extending through the middle of the local chords along the extension of the blade, provides a reduction of dispersion of aerodynamic loads along the length of the blade, which reduces aerodynamic loads acting on the propeller.

Fixing of the blades on each of the hubs inclinedly in a direction opposite to the rotation leads to the fact that an angle between an axis of the blade and a local speed of movement of the blade along a height becomes different from a direct angle, which leads to a reduction of a local aerodynamic resistance of the blade and, therefore, reduces aerodynamic loads acting on the propeller.

Provision of the propeller with an immovable cylindrical casing surrounding all blades and moved out forwardly of the blades of the front hub not less than by a length of the blade allows to increase a value of a torque. During the rotation the propeller throws air in a direction of rotation and forwardly against movement of the propeller. The thrown off air is reflected by the casing so that the running-on flow becomes twisted in a direction of their rotation, which increases a torque and thereby efficiency of the propeller. Due to the reflection of this air the maximum twist of the running-on flow is obtained with a cylindrical casing. A length of the casing is determined by a distance, over which a speed of the reflected air is close to zero. With optimal parameters of the blades and a speed of rotation of the propeller it becomes close to a radius of the propeller and therefore to a length of the blade.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG. 1 shows a general view of a propeller;

FIG. 2 — is a general view of the propeller with a casing;

FIG. 3 — is a side view of the propeller with the casing;

FIG. 4 — is a transverse cross-section of the blade;

FIG. 5 — is a view of a twisted blade from an end;

FIG. 6 — is a view of the propeller from the front with fixed blades inclined.

BEST MODE OF IMPLEMENTATION OF INVENTION

A propeller has a shaft 1 with at least two hubs 2 arranged on it with blades 3 fixed on each of the hubs uniformly over a circumference. A number of the hubs with the blades 3 can be different. The blades 3 on each subsequent hub 2 can be fixed both with a possibility of rotation in opposite direction, and with a possibility of rotation in one direction. The rotation can be performed from a motor by means of a drive shaft and gear trains.

Each blade 3 has a sharp front edge 4 and a sharp rear edge 5, and is configured along an extension of the blade 3 with a maximum thickness of profiles (0.10-0.25)b, wherein b is a length of a local chord of the blade 3.

In each blade 3 the maximum thickness 6 of the profile is located in a middle of each local chord.

The profiles can have different shapes, for example double-convex, wedge-like, rhombus-like. Along the extension the blades can be composed of profiles of different shapes.

Each blade 3 is twisted relative to an axis 8, extending through a middle of the local chord along the extension of the blade 3.

The blades can be fixed on each of the hubs 2 inclinedly in a direction opposite to the rotation of the propeller, as shown by arrow on FIG. 6.

The propeller can be provided with an immovable cylindrical casing 9 which surrounds all blades 3 and is moved out in front of the blades 3 of the front hub 2 not less than by length of the blade L. The hubs 2 with the blades 3 are driven in rotation by the shaft 1 of a motor, to generate aerodynamic forces and movements, which drive a vehicle into movement.

The provision of at least two hubs 2 with the blades 3 fixed on each of them uniformly over a circumference leads to a reduction of the sizes of the hubs 2 with the blades 3 which leads to a reduction of aerodynamic loads on the propeller.

Sharp front and rear edges 4 and 5 of each blade 3 together provide a reduction of aerodynamic resistance of the blades 3 and as a result a reduction of aerodynamic loads acting on the propeller.

The configuration along the extension of each blade 3 with the maximum thickness of the profiles (0.10-0.25)b, wherein b is a length of a local chord of the blade 3, provides within a selected range of the maximum thickness of the profiles a reduction of aerodynamic resistance of the blades 3 and as a result a reduction of aerodynamic loads acting on the propeller.

The maximum thickness 6 of the profile of each blade 3 located in a middle of each local chord 7 provides a uniform distribution of aerodynamic loads along the length of the chord 7 (width of the blade 3), which reduces aerodynamic loads acting on the propeller.

Twisting of each blade 3 relative to the axis 8, extending through the middle of its chord 7 along the extension of the blade 3, provides a reduction of a dispersion of aerodynamic loads along the length of the blade 3, which reduces aerodynamic loads acting on the propeller.

Fixing of the blades 3 on each of the hubs 2 inclinedly in a direction opposite to the rotation leads to the fact that the angle between the axis of the blade 3 and the local speed of movement of the blade 3 along the height becomes different from a direct angle, which leads to a reduction of local aerodynamic resistance of the blade 3 and, therefore, reduces the aerodynamic load on the propeller.

Provision of the propeller with the immovable cylindrical casing 10 surrounding all blades 3 and moved out in front of the blades 3 of the front hub 2 not less than by the length L of the blade 3 allows to increase a value of torque during the rotation of the propeller.

INDUSTRIAL APPLICABILITY

The present invention can be used most successfully in the area of aviation and a special transportation (air sled, air foil vessels). 

1-3. (canceled)
 4. A propeller, comprising a shaft; at least two hubs arranged on said shaft; blades fixed on each of said hubs uniformly over a circumference, each of said blades having sharp front and rear edges and configured along an extension of a corresponding one of said blades with a maximum thickness of profiles (0.10-0.25)b wherein b is a length of a local chord of said blade, and being twisted relative to an axis extending through a middle of said local chords along said extension of said blade, wherein said maximum thickness of said profile is located in the middle of each of said local chords.
 5. A propeller as defined in claim 4, wherein said blades are fixed on each of said hubs inclinedly in a direction opposite to a direction of rotation.
 6. A propeller as defined in claim 4; and further comprising an immovable cylindrical casing which surrounds all said blades and is moved out in front of said blades of a front hub not less than by length of said blade. 